System of cross-channel communication for effectors in an electric aircraft

Abstract

A system for cross-channel communication for effectors in an electric aircraft is presented. The system may include a flight component of an electric aircraft. The system may include a plurality of effectors, wherein the plurality of effectors may be configured to control the flight component. The system may include a plurality of flight controllers communicatively connected to the plurality of effectors, wherein the plurality of flight controllers may be configured to receive an input, generate a command as a function of the input and transmit the command to the plurality of effectors. The system may include a plurality of networks communicatively connected to the plurality of effectors and the plurality of flight controllers, wherein the plurality of networks may be configured to receive the command from the plurality of flight controllers and transmit the command to the plurality of effectors.

What is claimed is: 
     
       1. A system for cross-channel communication for effectors in an electric aircraft, wherein the system comprises:
 a flight component of an electric aircraft; 
 a plurality of effectors, wherein the plurality of effectors is configured to control the flight component and comprises a first effector and a second effector, wherein the first effector communicates with the second effector with cross-channel communication; 
 a plurality of flight controllers communicatively connected to the plurality of effectors, wherein the plurality of flight controllers is configured to:
 receive an input; 
 generate a command as a function of the input; and 
 transmit the command to the plurality of effectors; and 
 
 a plurality of networks communicatively connected to the plurality of effectors and the plurality of flight controllers, wherein the plurality of networks is configured to:
 receive the command from the plurality of flight controllers; and 
 transmit the command to the plurality of effectors. 
 
 
     
     
       2. The system of  claim 1 , wherein the electric aircraft is a fly-by-wire aircraft. 
     
     
       3. The system of  claim 1 , wherein the flight component comprises a control surface of the electric aircraft. 
     
     
       4. The system of  claim 1 , wherein the plurality of networks comprises a controller area network (CAN) bus. 
     
     
       5. The system of  claim 1 , wherein:
 the first effector is configured to receive the command from a first network of the plurality of networks and a second network of the plurality of networks; and 
 the second effector is configured to receive the command from the second network of the plurality of networks and a third network of the plurality of networks. 
 
     
     
       6. The system of  claim 5 , wherein:
 the first effector is configured to receive the command from the third network of the plurality of networks from the second effector using the cross-channel communication; and 
 the first effector is not directly connected to the third network of the plurality of networks. 
 
     
     
       7. The system of  claim 1 , wherein a network of the plurality of networks is communicatively connected to the plurality of effectors. 
     
     
       8. The system of  claim 1 , further comprising a sensor, wherein the sensor is configured to:
 detect that the first effector is disabled; and 
 generate a failure datum corresponding to the disablement of the first effector. 
 
     
     
       9. The system of  claim 1 , further comprising:
 the flight component comprises an electric motor; and 
 the plurality of effectors comprises an inverter, wherein the inverter controls the electric motor. 
 
     
     
       10. A method of cross-channel communication for effectors in an electric aircraft, wherein the method comprising:
 receiving, using a plurality of flight controllers, an input; 
 generating, using the plurality of flight controllers, a command as a function of the input; 
 communicatively connecting, using a plurality of networks, the plurality of flight controller and a plurality of effectors comprising a first effector and a second effector, wherein the first effector communicates with the second effector with cross-channel communication; and 
 transmitting, using the plurality of networks, the command from the plurality of flight controllers to the plurality of effectors. 
 
     
     
       11. The method of  claim 10 , wherein the electric aircraft is a fly-by-wire aircraft. 
     
     
       12. The method of  claim 10 , wherein the flight component comprises a control surface of the electric aircraft. 
     
     
       13. The method of  claim 10 , wherein the plurality of networks comprises a controller area network (CAN) bus. 
     
     
       14. The method of  claim 10 , further comprising:
 receiving, by the first effector, the command from a first network of the plurality of networks and a second network of the plurality of networks; and 
 receiving, by the second effector, the command from the second network of the plurality of networks and a third network of the plurality of networks. 
 
     
     
       15. The method of  claim 14 , further comprising receiving, by the first effector, the command from the third network of the plurality of networks from the second effector using the cross-channel communication, wherein the first effector is not directly connected to the third network of the plurality of networks. 
     
     
       16. The method of  claim 10 , wherein a network of the plurality of networks is communicatively connected to the plurality of effectors. 
     
     
       17. The method of  claim 10 , further comprising:
 detecting, using a sensor, that the first effector is disabled; and 
 generating, using the sensor, a failure datum corresponding to the disablement of the first effector. 
 
     
     
       18. The method of  claim 10 , further comprising:
 the flight component comprises a propulsor; and 
 the plurality of effectors comprises an inverter, wherein the inverter controls an electric motor of the propulsor.